Compression Molding Method and Reinforced Thermoplastic Parts Molded Thereby

ABSTRACT

A fiber reinforced part is formed from a compression molded thermoplastic resin reinforced with individual fibers of differing lengths randomly oriented substantially throughout the part.

TECHNICAL FIELD

This disclosure generally relates to compression molding techniques, anddeals more particularly with a method of compression molding fiberreinforced thermoplastics parts.

BACKGROUND

Various efforts have been directed toward replacing machined metal partswith lighter weight molded materials. For example, in the aircraftindustry, some metal parts have been replaced by plastic or compositeparts that are formed using any of a variety of techniques. In additionto weight savings, parts made of polymeric materials may be manufacturedmore economically, due in part to the reduction of machining time andmaterial waste.

Prior efforts to manufacture relatively high strength parts usingpolymeric materials have involved compression molding sheet-moldingcompounds, and laying up various forms of composite laminates usingthermoset materials. Each of these prior efforts may have disadvantages.For example, low viscosity thermoset materials have limited flowdistances during molding, and therefore may not be capable of producingparts of higher complexities. The use of sheet forms may not be suitablefor making parts that are small, complex or have changes in crosssectional geometries. Existing manufacturing techniques may also requirerelatively complex layups and/or complicated molds which may not be costeffective for some applications. Finally, polymeric parts made byexisting processes may not exhibit mechanical properties that aresubstantially the same in all directions. For example, laminated partsmay not possess the same mechanical strength in both the in-plane andthrough-the-thickness directions of the laminate. Similarly, moldedthermoset-resin chopped fiber parts may suffer from low mechanicalstrength in the through-the-thickness direction.

Accordingly, there is a need for a method of high flow compressionmolding high strength, complex polymeric parts that exhibit essentiallyisotropic or quasi-isotropic mechanical properties. There is also a needto replace machined metal parts with composite materials in order toreduce both part weight and manufacturing costs.

SUMMARY

In accordance with the disclosed embodiments, high flow compressionmolding of fiber reinforced thermoplastic resins reduces separation ofthe resin from the fibers during the molding process, thereby reducingresin-rich and resin-poor areas that may be undesirable. The moldingmethod produces at least near net shape carbon composite parts andfittings of complex geometries and tight dimensional tolerances. Thedisclosed method allows long flow lengths of the resin and fiber mixturethrough relatively complex mold passages, resulting in three dimensionalarrangements of fibers having differing lengths that promote isotropicproperties in the part. The disclosed method is relatively simple andmay eliminate the need for pre-forms by optimizing the shape of thefibers. The disclosed method is useful in compression molding a varietyof part features, including, but not limited to draft angles, ribs,cutouts, radii, holes, clevis and lugs, to name only a few. Therelatively high strength and toughness of the compression moldedthermoplastic parts allows metal inserts such as lugs and bushings to beincorporated into the part.

According to one disclosed embodiment, a method is provided of making acomposite part. The method includes producing a plurality of flakes eachcontaining fibers. A mold charge is formed by introducing the flakes anda thermoplastic resin into a mold. The charge is compression molded intoa part. Producing the flakes may include cutting each of the flakes fromfiber reinforced prepreg. The method may further comprise mixing flakesof at least two different shapes, wherein forming the charge includesintroducing the flakes of two different shapes into the mold. Thecompression molding method may include compressing the mold charge at arate that results in turbulent flow of the mold charge through the mold.The method may further comprise forming a hole in the molded part, andinstalling a metal hardware insert into the hole.

According to another disclosed embodiment, a method is provided ofmolding a fiber reinforced composite part. The method includes cutting aplurality of flakes from a unidirectional fiber perform pre-impregnatedwith a thermoplastic resin, and forming a mold charge by introducing apreselected quantity of the flakes into the mold. The method includescompression molding the mold charge into a mold cavity at a relativelyhigh flow rate that distributes the fiber substantially uniformlythrough the mold cavity with a substantially random fiber orientation.Cutting the flakes may include die cutting the flakes from a strip ofunidirectional prepreg tape. The flakes may be in the shape of one ormore of a square, a rectangle, a circle, an ellipse, a trapezoid, atriangle, a hexagon or a diamond.

According to a further embodiment, a reinforced composite part comprisesa compression molded thermoplastic resin having randomly oriented fiberof differing lengths providing multi-directional reinforcement. Thefibers are generally randomly oriented substantially throughout thepart. The part may further comprise at least one hole and a metalhardware insert secured within the hole. In one embodiment, the hole maybe threaded, and the hardware insert may include a HeliCoil®. The partsexhibit substantially quasi-isotropic properties.

The disclosed method of compression molding and the fiber reinforcedthermoplastic part produced thereby satisfies the need for a relativelylow cost manufacturing technique for producing reinforced thermoplasticparts of relatively complex geometries that exhibit substantiallyisotropic or quasi-isotropic properties.

BRIEF DESCRIPTION OF THE ILLUSTRATIONS

FIG. 1 is an illustration of a block diagram of a compression moldingprocess, including a perspective view of a reinforced thermoplastic partmolded thereby.

FIG. 2 is an illustration of a diagram showing a method of cutting fiberflakes used in reinforcing the thermoplastic part shown in FIG. 1.

FIG. 3 is an illustration showing typical shapes for the flakes.

FIG. 3A is an illustration of a fiber flake showing the presence ofdiffering fiber lengths.

FIG. 4 is an illustration of a flow diagram of a method of compressionmolding a fiber reinforced thermoplastic part, optionally havinghardware inserts.

FIGS. 5, 6, 7 and 8 are illustrations of perspective views of typicalfiber reinforced thermoplastic parts produced by the disclosed moldingmethod.

FIG. 9 is an illustration of a sectional view of a compression moldedpart showing the part's complex fiber microstructure.

FIG. 10 is an illustration of a diagram showing an open compression moldbeing charged with prepreg fiber flakes in preparation for molding apart.

FIG. 11 is an illustration of a sectional view showing the mold of FIG.10 having been closed to mold the charge.

FIG. 12 is an illustration of a sectional view showing the flow of amold charge through a portion of a mold cavity.

FIG. 13 is an illustration of an exploded orthogonal view of acompression molded thermoplastic part having a tapped hole for receivinga HeliCoil® insert and a threaded bolt.

FIG. 14 is an illustration of a flow diagram of aircraft production andservice methodology.

FIG. 15 is an illustration of a block diagram of an aircraft.

DETAILED DESCRIPTION

Referring first to FIG. 1, the disclosed embodiments relate to a methodof high flow compression molding a fiber reinforced thermoplastic part20 using a compression molding machine 22. The molding machine 22includes a mold 22 a having a mold cavity 22 b into which a mold charge60 is introduced. The mold charge 60 comprises randomly oriented fiberflakes 24. As used herein, “high flow” molding refers to flow of themold charge 60 over relatively long distances though the mold cavity 22b, where “long distances” refers to distances that are multiples of themaximum length dimension of an individual flake 24. Also, as usedherein, “flakes” and “fiber flakes” refer to individual pieces,fragments, slices, layers or masses that contain fibers suitable forreinforcing the part 20.

As will be discussed later in more detail, in one embodiment, the moldcharge 60 may comprise only fiber flakes 24 that are formed from aunidirectional fibers pre-impregnated with a thermoplastic resin. Inthis embodiment, the source of the thermoplastic resin which forms thatpart 20 is derived solely from the resin contained in the flakes 24.Alternatively, in another embodiment, it may be possible to usetackified dry fiber flakes 24 that may not be pre-impregnated withresin, in which case a premeasured quantity of thermoplastic resin 26may added to the charge 60.

The flakes 24 have one or more specific shapes which aid in maintaininga substantially uniform distribution and random orientation of thereinforcing fibers 33 (see FIGS. 3 and 4) within the melted mixture ofresin and reinforcing fibers as the melted mixture of fibers andthermoplastic resin flows through various features, constrictions andextremities (all not shown) within the mold cavity 22 b. The specificshapes of the flakes 24 also assist in imparting quasi-isotropicmechanical properties to the part 20 by incorporating various lengths offiber reinforcement within the mixture. The thermoplastic resin whicheither forms part of the flakes 24 or which is added to dry flakes 24,may comprise a relatively high viscosity thermoplastic resin such as,without limitation, PEI (polyetherimide) PPS (polyphenylene sulphide),PES (polyethersulfone), PEEK (polyetheretherketone), PEKK(polyetheretherketone), and PEKK-FC (polyetherketoneketone-fc grade), toname only a few. The reinforcing fibers in the flakes 24 may be any of avariety of high strength fibers, such as, without limitation, carbon,metal, ceramic and/or glass fibers. It may also be possible to reinforcethe part 20 by adding metallic and/or ceramic particles or “whiskers” tothe mold charge 60.

As will be discussed below, the mold charge 60 is subjected to heat andpressure in the compression molding machine 22 which result inrelatively fast flow rates of the melted resin and fiber mixture thatmay approach or achieve turbulence at least in some parts of the moldcavity 22 b, especially when combined with mold wall effects.Optionally, the part 22 may have hardware inserts formed from any ofvarious metals, which are either molded into the part 20 as part of themolding process, or are installed after the part 20 has been molded.

Referring to FIG. 2, the flakes 24 may be, for example and withoutlimitation, formed by die cutting individual flakes 24 from a roll 27 ofunidirectional prepreg tape 25 having a backing 25 a using a cutting die29. Alternatively, as previously mentioned, it may be possible to formthe flakes 24 from a tackified dry fiber perform (not shown), as by diecutting or other techniques. The cutting die 29 may include a stationaryportion 29 a which supports the tape 25 while a matching reciprocatingdie member 29 b cuts the flake 24 from the tape 25. The backing 25 a maybe taken up on a second roll (not shown). Alternatively, the flakes 24may be cut from a sheet (not shown) of unidirectional prepreg. It mayalso be possible to form the flakes 24 using other production processes.

The flakes 24 may be substantially flat and may have any of variousoutline shapes. For example, as shown in FIG. 3, the flakes 24 may havethe shape of a square 24 a, a rectangle 24 b, a circle 24 c, anequilateral triangle 24 d, a trapezoid 24 e, a hexagon 24 f or otherpolygon (not shown), an ellipse 24 g or a diamond 24 h. Other shapes arepossible. In some embodiments, flakes 24 with two or more of the shapes24 a-24 h may be mixed together with the thermoplastic molding compound26 in order to provide a mixture having fibers 33 of differing lengths.

The presence of fibers 33 having differing lengths in the mixture aidsin achieving a more uniform distribution of the flakes 24 in the part20, while promoting isotropic mechanical properties and/or strengtheningthe part 20. Flakes 24 having shapes such the circle 24 c, triangle 24d, hexagon 24 f, ellipse 24 g and diamond 24 h, may be particularlyuseful in improving the isotropic mechanical properties of the part 20because of the fact that these shapes result in each flake 24 havingdiffering fiber lengths. For example, as shown in FIG. 3A, the fibers 31near the top and bottom of the flake 24 g have a length L₁ that isconsiderably shorter than the length L₂ of the fibers 33 near the middleof the flake 24 g. Long fibers 33 may provide high strength in aparticular direction, while shorter length fibers 31 allow the flakes 24to be more easily formed into complex three dimensional arrangements.Accordingly, a combination or mix of long and short fiber lengths withina single flake 24 may be particularly desirable. Generally, the size andshape of the flakes 24 may be selected to optimize the flow, strengthand finish quality of the part 20.

Referring now to FIG. 4, the part 20 described above may be manufacturedusing one embodiment of a method that begins at step 28 with providing atape or sheet of unidirectional fiber prepreg, or in other embodiments,a tackified dry fiber preform. At step 30, the flakes 24 may be cut fromthe tape or sheet to the desired outline shape. At step 32, a moldcharge 60 (FIG. 1) is formed by measuring, typically by weighing, aquantity of the flakes 24 that is to form the charge 60 for a particularpart 20. In those cases where the flakes 24 are made from a tackifieddry perform, a quantity of the thermoplastic resin 26 is also weighedwhich is to form part of the charge 60.

The mold charge 60 consisting of the premeasured quantity of the flakes24 (and optionally, the premeasured thermoplastic resin) is loaded intothe mold 22 a, such the fiber orientations of the flakes 24 aresubstantially random. In those embodiments where the fiber flakes 24 arederived from a tackified dry fiber preform and it is necessary toseparately add thermoplastic resin 26 to the charge 60, it may bedesirable to arrange the flakes 24 and the resin 26 in multiple,alternating layers within the mold 60 to aid in mixing of resin 26 withthe dry fiber flakes 24 during the molding process. At step 36, the moldcharge 60 is compression molded to produce a relatively high rate offlow of the charge throughout the mold cavity 22 b (FIG. 1). The flowrate of the mold charge 60 through the mold cavity 22 b will depend theamount of heat and pressure that is applied during the molding processwhich in turn may be dictated by the particular application.

In those cases where the part 20 includes hardware inserts 42, anadditional set of steps 37, 39 and 41 may be performed. At step 37, oneor more holes are formed in the molded part 20, either by molding theholes into the part 20 or by a machining process such as drilling thepart 20 after the part has been removed from the mold 22 a (FIG. 1). Inthose cases where the hardware insert 42 may include threads, then thehole is tapped at 39, following which the hardware insert 42 may beinstalled at step 41.

FIGS. 5, 6, 7 and 8 illustrate typical parts having relatively complexfeatures that may be compression molded using the disclosed moldingmethod. FIG. 5 illustrates a fitting 20 a having integrally moldedraised bosses 38 and bushing inserts 42. FIG. 6 illustrates a horizontaldoubler 20 b having molded-in, countersunk holes 40 and nut plateinserts 44. FIG. 7 illustrates a pivot fitting 20 c having thinlytapered extremities 39 and molded-in countersunk holes 40. FIG. 8illustrates a load transfer bar 20 d having molded-in bushings 42.

FIG. 9 illustrates, on a magnified scale, the relatively complex fibermicrostructure of a part 20 manufactured by the disclosed compressionmolding method which results from use of relatively high viscositythermoplastics and the extended distances over which the mold charge 60(FIG. 1) is made to flow with causing separation of the fibers 31, 33.The high viscosity of the thermoplastic molding resin tends to carry thereinforcing fibers 31, 33 along with the resin flow throughout the moldcavity 22 b (FIG. 1) and may maintain the flakes substantially evenlydistributed, rather than allowing the concentration of the flakes in anyparticular area to become too high or too low. The relatively uniformdistribution of the fibers 31, 33 in the finished part 20 results inpart from the fact that the fibers 33 are initially distributeduniformly in their prepreg state before the resin in the flakes 24 meltaway. The relatively complex fiber microstructure shown in FIG. 9, inwhich the fibers 31, 33 are distributed substantially uniformly withsubstantially random fiber orientations, results in the part 20exhibiting substantially isotropic or quasi-isotropic mechanicalproperties and relatively complex failure modes.

FIGS. 10 and 11 illustrate apparatus for carrying out steps 32, 34 and36 shown in FIG. 4. A compression mold 52 includes first and second moldportions 52 a, 52 b which may respectively have mold surfaces 56 a, 56 bcorresponding to the shape of the desired part 20 (FIG. 1). The mold 52includes a mold cavity 58 formed at least in part by the mold surfaces56 a, 56 b. The mold 52 may include heating elements 54 for heating themold 52 to the desired temperature. As shown in FIG. 10, with the mold52 open, a premeasured quantity of prepreg flakes 24 may be introducedfrom a reservoir 48 into the mold portion 52 a. The premeasured flakes24 are loaded into the mold cavity 58 such that they are randomlyoriented.

As shown in FIG. 11, the application of a force F through a ram 62 tothe mold section 52 b forces the mold portions 52 a, 52 b together,thereby compressing the mold charge 60 within the mold cavity 58. Thefibers 24 may be only randomly distributed in two planes when they areinitially placed in the mold 22 a, however, once the resin melts in theflakes 24 melts to release the fibers 31, 33, the long flow distanceswithin the mold cavity 22 b “encourages” the fibers 33 (FIG. 3A) todistribute themselves into a complex, three dimensional, interlockingarrangement, caused by obstacles, bends, friction against the mold 22 a,etc. The combination of the pressure and heat applied to the charge 60results in the mixture of melted resin and individual fibers 31, 33flowing over relatively long distances throughout the mold cavity 58. Asthe resin flows through the mold cavity 58, the flakes 31, 33 arecarried along with the resin so as to be substantially uniformlydistributed throughout the mold cavity 58, and substantially randomlyoriented. Eventual cooling of the mold 52 results in consolidation ofthe thermoplastic resin, leaving the differing lengths of fibers 33(FIG. 3A) originating from the flakes 24 integrated within theconsolidated resin, with random orientations.

FIG. 12 graphically illustrates the flow of the charge 60 around anglefeatures 64 of a mold cavity 58 having a tapered extremity 66. The flowmay include turbulent components 68 that aid in maintaining asubstantially uniform mixture and distribution of the fibers 31, 33within the flowing resin so as to avoid resin or fiber rich, or resin orfiber poor areas within the finished part 20.

FIG. 13 illustrates the installation of a HeliCoil® insert 70 into atypical thermoplastic part 20 made according to the disclosedembodiment. A hole 71 is formed in the part 20 as by drilling ormolding. The hole 71 is then tapped to form a set of thermoplastic,internal threads 72 within the hole 71. Next, the HeliCoil® insert 70,which comprises a helically shaped metal coil 74, is wound into thethermoplastic threads 72 in the hole 71. Once installed in the hole 71and seated within the thermoplastic internal threads 72, the metal coil74 provides a set of metal, female (internal) threads 75 within the hole71 that may threadably receive the male (external) threads 77 of anotherpart (not shown) or a fastener such as a bolt 79.

Embodiments of the disclosure may find use in a variety of potentialapplications, particularly in the transportation industry, including forexample, aerospace, marine and automotive applications. Thus, referringnow to FIGS. 14 and 15, embodiments of the disclosure may be used in thecontext of an aircraft manufacturing and service method 76 as shown inFIG. 14 and an aircraft 78 as shown in FIG. 15. During pre-production,exemplary method 76 may include specification and design 80 of theaircraft 78 and material procurement 82 in which the disclosed parts 20may be specified for use in components and assemblies on the aircraft78. During production, component and subassembly manufacturing 84 andsystem integration 86 of the aircraft 78 takes place. The disclosedcompression molding method may be used to produce parts and componentsthat are assembled during processes 84, 86. Thereafter, the aircraft 78may go through certification and delivery 88 in order to be placed inservice 90. While in service by a customer, the aircraft 78 is scheduledfor routine maintenance and service 92 (which may also includemodification, reconfiguration, refurbishment, and so on). The disclosedmethod may be used to parts 20 that are installed during the maintenanceand service 92.

Each of the processes of method 76 may be performed or carried out by asystem integrator, a third party, and/or an operator (e.g., a customer).For the purposes of this description, a system integrator may includewithout limitation any number of aircraft manufacturers and major-systemsubcontractors; a third party may include without limitation any numberof vendors, subcontractors, and suppliers; and an operator may be anairline, leasing company, military entity, service organization, and soon.

As shown in FIG. 15, the aircraft 78 produced by exemplary method 76 mayinclude an airframe 94 with a plurality of systems 96 and an interior98. The disclosed method may be used to produce parts 20 that form partof, or which may be installed on the airframe 94. Examples of high-levelsystems 96 include one or more of a propulsion system 100, an electricalsystem 102, a hydraulic system 104, and an environmental system 106. Anynumber of other systems may be included. Although an aerospace exampleis shown, the principles of the disclosure may be applied to otherindustries, such as the marine and automotive industries.

The disclosed molding method may be employed to mold parts during anyone or more of the stages of the production and service method 76. Forexample, components or subassemblies corresponding to production process84 may incorporate composite parts that are produced using the disclosedmolding method. Also, one or more method embodiments, or a combinationthereof may be utilized during the production stages 84 and 86, forexample, by substantially expediting assembly of or reducing the cost ofan aircraft 78.

Although the embodiments of this disclosure have been described withrespect to certain exemplary embodiments, it is to be understood thatthe specific embodiments are for purposes of illustration and notlimitation, as other variations will occur to those of skill in the art.

1. A method of making a composite part, comprising: producing aplurality of flakes each containing fibers; forming a mold charge,including introducing the flakes and a thermoplastic resin into a mold;and, compression molding the charge into a part.
 2. The method of claim,1, wherein producing the flakes includes cutting each of the flakes fromfiber reinforced prepreg.
 3. The method of claim, 1, further comprising:mixing flakes of at least two different shapes respectively havingfibers of differing lengths, and wherein forming the charge includesintroducing the flakes of two different shapes into the moldingcompound.
 4. The method of claim, 1, wherein the compression moldingincludes compressing the mold charge at a rate that results in turbulentflow of the mold charge through the mold.
 5. The method of claim, 1,wherein the thermoplastic resin is one of: PEI, PPS, PES, PEEK, PEKK,and PEKK-FC.
 6. The method of claim 1, wherein: producing the flakesincludes cutting each of the flakes from a dry fiber preform, andintroducing the thermoplastic resin into the mold is performedseparately from introducing the flakes into the mold.
 7. The method ofclaim 1, further comprising: forming a hole in the molded part,installing a hardware insert into the hole.
 8. The method of claim 7,wherein: the hole is formed by drilling, and inserting the hardwareincludes tapping threads in the part within the hole and threading aninsert into the hole.
 9. The method of claim 1, wherein the fibers arepre-impregnated with the thermoplastic resin.
 10. A composite part madeby the method of claim
 1. 11. A method of molding a fiber reinforcedcomposite part, comprising: cutting a plurality of flakes from aunidirectional fiber preform pre-impregnated with a thermoplastic resin;forming a mold charge by introducing a preselected quantity of theflakes into a mold; and, compression molding the mold charge in a moldcavity.
 12. The method of claim 11, wherein cutting the flakes includesdie-cutting the flakes from a strip of unidirectional prepreg tape. 13.The method of claim 11, wherein at least certain of the flakes each havethe shape of one of: a square, a rectangle, a circle, an ellipse, atrapezoid, a triangle, a hexagon, and a diamond.
 14. The method of claim11, wherein at least certain of the flakes include fibers havingdiffering lengths.
 15. The method of claim 11, wherein the thermoplasticis one of: PEI, PPS, PES, PEEK, PEKK, and PEKK-FC.
 16. A reinforcedcomposite part, comprising: a compression molded thermoplastic resinhaving randomly oriented fibers of differing lengths providingmulti-directional reinforcement.
 17. The reinforced composite part ofclaim 16, wherein the thermoplastic is one of: PEI, PPS, PES, PEEK,PEKK, and PEKK-FC
 18. The reinforced composite part of claim 16, whereinthe fibers are carbon fibers and are distributed substantially uniformlysubstantially throughout the resin.
 19. The reinforced composite part ofclaim 16, wherein the flakes have at least one of the following shapes:a square, a rectangle, a circle, an ellipse, a trapezoid, a hexagon, anda triangle.
 20. The reinforced composite part of claim 16, wherein theflakes include at least two differing shapes.
 21. The reinforcedcomposite part of claim 16, further comprising: at least one hole in thecompression molded thermoplastic resin: and a metal hardware insertsecured within the hole.
 22. The reinforced composite part of claim 21,wherein: the hole is threaded, and the hardware insert includes aHeliCoil®.
 23. The reinforced composite part of claim 11, wherein thepart exhibits substantially quasi-isotropic properties.
 24. A method ofmaking a composite aircraft part, comprising: cutting a plurality offirst flakes from a unidirectional carbon fiber thermoplastic prepregtape, each of the first flakes having a first shape; cutting a pluralityof second flakes from a unidirectional carbon fiber thermoplasticprepreg tape, each of the second flakes having a second shape differentthan the first shape; introducing the first and second flakes into amold having a mold cavity substantially conforming to the shape of thepart; and, compression molding the charge, including applying heat andpressure to the charge that results in a relatively high flow rate ofthe charge through the mold cavity, such that the combination of theflow rate and the viscosity of the charge result in the fibers in theflakes being distributed substantially uniformly through the mold cavitywith substantially random fiber orientations.
 25. A carbon fiberreinforced composite aircraft part exhibiting substantially isotropicmechanical properties, comprising: a compression molded thermoplasticresin having at least one hole therein; a plurality of reinforcingfibers molded into the molded resin, the fibers being distributedsubstantially uniformly throughout the molded resin and havingsubstantially random orientations, the fibers having differing lengths;and at least one metal hardware insert secured within the hole.